2nd International Symposium on NDT in Aerospace 2010 - We.2.A.2 Visualization of CFRP Structures Based on Acoustic Techniques for NDT Dieter HENTSCHEL*, Sabine GOLDBACH**, Rita BULGRIN***, Thomas WERNER**** * Fraunhofer IZFP, Maria-Reiche-Str. 2, 01109 Dresden ** IMA Dresden, Wilhelmine-Reichard-Ring 4, 01109 Dresden *** Cotesa GmbH, Bahnhofsstr. 67, 09648 Mittweida **** Werner Industrielle Elektronik, Alte Straße 2, 01731 Kreischa Abstract. The constant growth of air traffic leads to increasing demands for the aircraft industry to manufacture airplanes more economically and to ensure a higher level of efficiency, ecology and safety. During the last years important improvements for fuselage structures have been achieved by application of new construction principles, employment of sophisticated and/or alternative materials, and by improved manufacturing processes. In particular the intensified application of fibre-reinforced plastics components is in the focus of current discussions and research. The introduction of new materials and design concepts for new types of aircraft structures requires a large number of material tests starting from coupon test through component tests (shell, barrel) to full scale testing of complete aircraft structures. Tests of all levels of complexity require a large number and wide spectrum of NDE inspections. Especially in multilayer structures of carbon fibre-reinforced plastics (CFRP) many challenges have to be met until a reliable and accurate determination of relevant defects is obtained. The main goal of a national Saxony project is to improve the existing ultrasonic test technology in such a way that it is optimally suited for the examination of CFRP multilayer structures. So the several layers of CFRP shall be scanned by ultrasonic beam to visualize the layers. In combination of ultrasonic phased array and 3-Dtomography the internal state of material will be shown. In this way manufacturing defects, f.i. missing fibres, wrong manufactured laminates as well as material defects (delaminations, fibre breaks) will be detected. The B-Scan and C-Scan results are then used for the visualization of individual layers and the complete layer set-up. In the project special CFRP specimen with manufacturing defects were produced in RTM- and Autoclav processing at IMA Dresden and Cotesa Mittweida. At laboratory tests at IZPP Dresden could be determined, that with carefully selected transducers and frequencies the detection of defects and irregularities in the layer structure like delaminations, fibre cracking, ondulations, missing layers etc. and even to visualize the fibre orientations in the individual layers were possible. In comparison to common ultrasonic technique (immersion technique, phased array technique), carried out by IMA Dresden and Cotesa Mittweida, the high sensibility of the new technique was defined. Such a sensibility was reached. License: http://creativecommons.org/licenses/by/3.0/ 1
1. INTRODUCTION The constant growth of air traffic leads to increasing demands for the aircraft industry to manufacture airplanes more economically and to ensure a higher level of efficiency, ecology and safety. During the last years important improvements for fuselage structures have been achieved by application of new construction principles, employment of sophisticated and/or alternative materials, and by improved manufacturing processes. In particular the intensified application of fibre-reinforced plastics components is in the focus of current discussions and research. The introduction of new materials and design concepts for new types of aircraft structures requires a large number of material tests starting from coupon test through component tests (shell, barrel) to full scale testing of complete aircraft structures. Tests of all levels of complexity require a large number and wide spectrum of NDE inspections. To fulfil the rigorous requirements for aerospace NDT, conventional nondestructive evaluation (NDE), e.g. high frequency ultrasonic testing, infrared thermography, eddy current testing, x-ray CT, and visual inspection, are generally applied to aerospace material. In this context the probability of detection (POD) for the various methods and possible damages is of particular importance for the NDE pyramid. Especially in multilayer structures of carbon fibre-reinforced plastics (CFRP) many challenges have to be met until a reliable and accurate determination of relevant defects is obtained. Anisotropy, inhomogeneity and not exactly recordable electrical conductivity are problematic characteristics of these materials. Therefore in many cases eddy current and magnetic methods cannot be used. The classical X-ray technology is also not applicable since the density contrast is usually too small. Infrared thermography is able to detect the presence of larger defects but its depth resolution is not sufficient to resolve the exact layer structure. One of the most promising NDE methods for CFRP multilayers is represented by the ultrasonic pulse-echo technique. This method can be used with different transducers and frequencies and thus, an optimal tradeoff between penetration depth on the one hand and lateral and depth resolution on the other hand can be obtained in many cases. The main goal of an ongoing national project is to improve the existing ultrasonic test technology in such a way that it is optimally suited for the examination of CFRP multilayer structures. The B-Scan and C-Scan results are then used for the visualization of individual layers and the complete layer set-up. First results of the project revealed that with carefully selected transducers and frequencies it is possible to detect defects and irregularities in the layer structure like delaminations, fibre cracking, ondulations, missing layers etc. and even to visualize the fibre orientations in the individual layers. 2. HARDWARE: IZFP S ULTRASONIC EVALUATION SYSTEM The hardware used for the described experiments based on a multichannel ultrasonic NDE system, which was developed and manufactured in our institute. This test device can operate not only as a multichannel ultrasonic device with up to 64 channels, but also as a phased array system in two different modes as well. The miniaturized device is well suited for automated test procedures, because it is able to localize near the ultrasonic transducers. Figure 1 shows two types of our device: On the left hand side the device has a standard HYPERTRONICS interface to connect a usual phased array transducer. The device on the right hand side is configured to operate with up to 64 single ultrasonic transducers. 2
Fig. 1: IzfP s ultrasonic evaluation system In general, the ultrasonic evaluation system has the following features: Computer interface: USB 2.0 High Speed, max. 40MByte/s data transfer rate Miniaturized geometrical dimensions (190x190x65mm³) Sensor near setup Designed for up to 64 element array-transducers Phased Array or Sampling Phased Array techniques Also useable for multi-channel ultrasound applications Frequency range: 500kHz to 30MHz (-3dB) A/D converter: 14 bit (13 bit + sign), up to 100MS/s The measuring system meets DIN EN 12668 part 1 and operates with a device driver for Windows XP, Windows Vista and Windows 7 (x86 and x64) and a managed Windows API, based on.net 3.5 framework as well. 3. TEST SETUP Besides the ultrasonic frontend system PCUS pro Array developed by IZFP-D and decribed in point 2, a 16-elements Sensor Line Array with signal frequency of 10 MHz and a 4-axis mechanical manipulator system was used as an experimental test system. Figure 2 shows on the left hand side the mechanical scanning system and on the right hand side a detail of this configuration with the sensor line array transducer. Fig. 2: Test setup: Mechanical scanner The following figure 3 illustrates the used ultrasonic frontend system PCUS pro array on the left hand side with the transducer connector and the connected trigger 3
interface. (The USB connection on the back side is hardly visible.) On the right hand side, a 16 channel transducer is seen, which is manufactured by our institute to meet the needs for CFRP testing optimally. Fig. 3: Test setup: Frontend electronics and transducer 4. TEST RESULTS: C-SCANS, B-SCANS In our experiments, CFRP specimens, manufactured by IMA Dresden in RTM technology, with following properties were examined first: Dimensions [mm]: 200*200*3,1 Layers: 10 Fig. 4 shows the principle of manufactured specimen. Fig. 4: CFRP specimen The figures below show on the left hand side the complete data evaluation with A-, B- and C-Scan and on the right hand side the increased C-Scan each. Figure 5 shows the ultrasonic data of a defect-free CFRP specimen. Figure 6, 7, 8 show the ABC-Scan of CFRP plates with artificial defects, caused by cutting of an inner layer, by ondulation of an inner layer and by fiber roving in two inner layers. Fig. 5: Defect-free CFRP specimen 4
Fig. 6: CFRP specimen with cutting of inner layer 3 Fig. 7: CFRP specimen with Ondulation of 3rd Inner Layer Fig. 8: CFRP specimen with fiber roving in 2nd and 3rd inner layer In the next step, a CFRP plate with artificial defects inside was manufactured by project partner IMA. For this reason, quadratic polymer foils (single and double foils of different materials) were laminated in an inner layer, which have to be found by ultrasonic method. At first common ultrasonic investigations (immersion technique, phased array technique) were carried out at IMA. Fig. 9 shows the comparison between C-scans from immersion technique (ScanMaster LS 100, 5 MHz) and phased array technique (Omniscan RDTech, 5 MHz). 5
Fig. 9: C-Scans of immersion technique (upper fig.) and phased array (lower fig.) Inside an IZFP lab, the CFRP plate was scanned with a 10MHz ultrasonic transducer. Figure 10 shows the ultrasonic C-scans in several layers. Fig. 10: CFRP specimen with polymer foils in inner layer The following investigations were undertaken with a praxis relevant part, produced by the project partner COTESA in autoclav technology. This structure is a stringer part with a layer thickness of about 300µm, fig. 11. Fig. 11: Stringer part with artificial damages Based on common ultrasonic phased array investigations (Omniscan RDTech, 5 MHz) IMA could detect the damages, fig. 12. 6
Fig. 12: C-Scan ultrasonic phased array Therefore, the ultrasonic testing of the structure has many challenges. Nevertheless, we have produced ultrasonic B-scans by different focusing of ultrasonic beam. Figure 13 shows such a B-scan with the CFRP layers in the edge region. Fig. 13: B scan of CFRP structure Fig. 14 shows the stringer scan combined with the micrograph. The stringer crotch is visualised much better than based on common ultrasonic technique. Fig. 14: Stringer Scan combined with micrograph for layer orientation 7
5. SUMMARY, FUTURE STEPS Picture-giving evaluation procedures with Sampling Phased array (SPA) in connection with a mechanical scanner are suitable for the characterisation of CFRP structures B Scans and C scans show orientation of any layer and defects in it as ondulations, missing fibers etc. There were developed a container data format and a program for three-dimensional visualisation of measurement results based on ultrasonic systems A platform for WHQL-certification of software were developed and successfully used. test procedures took place with 10MHz/16 elements array transducer, at different scanner speeds (values: 10 to 100 mm/s) Future tests are planned with 20MHz/16(64) elements array transducer with higher scanner speed A precise mechanical scanner (accuracy +/- 0,05 mm) for US testing of large 3- dimensional CFRP structures (x: 2420 mm, y: 1760mm, z: 1350mm) is under development ACKNOWLEGDEMENTS This work has been supported by the German Saxony State Ministry for Economic Affairs and Labor within the framework of the joint project CFKvis, grant number 12767/2123. Special thanks to B. Lamek and C. Richter. REFERENCES 1. D. Hentschel, Visualization of Aviation Relevant CFRP Structures, Fraunhofer IZFP, Annual Report 70-71, 2008 2. A. Bulavinov, Sampling Phased Array Ultrasonic Testing with Inverse Phase Matching for Carbon Fiber Structures, Fraunhofer IZFP, Annual Report 68-69, 2008 3. D. Hentschel, Verfahren zur Visualisierung des Lagenaufbaus von Bauteilen aus faserverstärktem Kunststoff (CFKvis), final SAB-report no. 12766/2123, IZFP Dresden, 2010 4. Th. Werner, Auswertesoftware zur 3D-Visualisierung des Lagenaufbaus von Bauteilen aus faserverstärktem Kunststoff, final SAB-report no. 12766/2123, Werner Industrielle Elektronik Kreischa, 2010 5. S. Goldbach, Werkstoffmodellierung und Verfahrensqualifikation von Visualisierungs- Systemen, final SAB-report no. 12766/2123, IMA Dresden, 2010 6. R. Bulgrin, Fertigungsbedingte Imperfektionen in Faserverbundwerkstoffen, final SAB-report no. 12766/2123, Cotesa GmbH Mittweida, 2010 8